Parallel hybrid-electric aircraft engine

ABSTRACT

A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer neede

RELATED APPLICATIONS

The present application is a continuation-in-part application of U.S. provisional patent application, Ser. No. 62/375,171, filed Aug. 15, 2016, for PARALLEL HYBRID-ELECTRIC AIRCRAFT ENGINE, by Marinus Bernard Bosma, included by reference herein and for which benefit of the priority date is hereby claimed.

FIELD OF THE INVENTION

The present invention relates to hybrid power plants and, more particularly, to a parallel hybrid-electric powerplant aircraft engine.

BACKGROUND OF THE INVENTION

Aircraft go through phases of flight, commonly, takeoff, climb, cruise, descent and landing. For the takeoff and climb portion of the flight the aircraft engine is required to generate enough horsepower to accelerate and lift the aircraft to altitude. The physics of the problem is that power is needed to accelerate the mass of the aircraft and then once free from the runway additional power is needed to lift the aircraft against the force of gravity. Once at a given altitude and no longer climbing or accelerating the engine need only overcome the drag on the aircraft. This disproportionate power requirement means the aircraft needs to have a large powerplant that can perform the functions of accelerate and climb but then reduce power to that required to maintain level flight.

The amount of power delivered by the typical engine is proportional to its weight. Therefore, an engine capable of getting an aircraft to it's cruise altitude would be heavier than an engine used to maintain level flight. The additional weight of the powerful engine, then must be carried by the aircraft even though it's not yielding power from the additional weight.

An engine that can be both lightweight and powerful would allow this.

Serial Hybrid-Electric Aircraft engines which are a generator to provide power via wires to an electric motor turning a propeller.

Serial Hybrid-Electric Aircraft engines can fail if the generator fails and battery power is lost. Serial Hybrid-Electric Aircraft engines can fail if the circuit between the generator and the propeller motor breaks. Serial Hybrid-Electric Aircraft engines can fail if the motor fails. Serial Hybrid-Electric Aircraft engines can fail if the engine on the generator fails. would be advantageous to provide an aircraft powerplant that can accelerate an aircraft to takeoff speed.

It would also be advantageous to provide an aircraft powerplant that can provide excess horsepower for climb.

It would further be advantageous to provide aircraft powerplant that throttle back to that power necessary for cruise flight.

It would further be advantageous to provide aircraft powerplant that has good fuel economy by operating at maximum efficiency power settings.

It would further be advantageous to provide aircraft powerplant that uses two different sources of power as a backup if one or the other fails.

SUMMARY OF THE INVENTION

In accordance with the present invention, there is provided a parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.

BRIEF DESCRIPTION OF THE DRAWINGS

A complete understanding of the present invention may be obtained by reference to the accompanying drawings, when considered in conjunction with the subsequent, detailed description, in which:

FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine;

FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine;

FIG. 3 is a left view of a parallel hybrid-electric aircraft engine;

FIG. 4 is a front view of a parallel hybrid-electric aircraft engine;

FIG. 5 is a top view of a parallel hybrid-electric aircraft engine; and

FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine.

For purposes of clarity and brevity, like elements and components will bear the same designations and numbering throughout the Figures.

DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 2 is a lower perspective view of parallel hybrid electric engine showing the internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50 and propeller 20. FIG. 3 is a left side view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 4 is a front view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, sprag clutch 30, flexible belt 40, electric motor 50, engine output shaft 60 and propeller 20. FIG. 5 is a top view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20. FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10, flexible belt 40, electric motor 50 and propeller 20.

Since other modifications and changes varied to fit particular operating requirements and environments will be apparent to those skilled in the art, the invention is not considered limited to the example chosen for purposes of disclosure, and covers all changes and modifications which do not constitute departures from the true spirit and scope of this invention.

Having thus described the invention, what is desired to be protected by Letters Patent is presented in the subsequently appended claims. 

What is claimed is:
 1. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: means for provide power for takeoff and climb in parallel with an electric motor; means for thrust; means for transferring power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; means for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, and rigidly connected to said means for thrust; and means for transferring rotary motion to the sprag clutch, rigidly connected to said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure, and rigidly connected to said means for provide power for takeoff and climb in parallel with an electric motor.
 2. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for provide power for takeoff and climb in parallel with an electric motor comprises a gasoline or diesel internal combustion engine.
 3. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for thrust comprises a variable pitch propeller.
 4. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure comprises an over-running sprag clutch.
 5. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor comprises a ribbed flexible belt.
 6. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries comprises an out-runner electric motor.
 7. The parallel hybrid-electric aircraft engine in accordance with claim 1, wherein said means for transferring rotary motion to the sprag clutch comprises an engine output shaft.
 8. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: a gasoline or diesel internal combustion engine, for provide power for takeoff and climb in parallel with an electric motor; a variable pitch propeller, for thrust; an over-running sprag clutch, for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; a ribbed flexible belt, for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said sprag clutch; an out-runner electric motor, for transmit rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said flexible belt, and rigidly connected to said propeller; and an engine output shaft, for transferring rotary motion to the sprag clutch, rigidly connected to said sprag clutch, and rigidly connected to said internal combustion engine.
 9. A parallel hybrid-electric aircraft engine for providing power to a propeller-driven aircraft, comprising: a gasoline or diesel internal combustion engine, for provide power for takeoff and climb in parallel with an electric motor; a variable pitch propeller, for thrust; an over-running sprag clutch, for transfer power from internal combustion engine to the propeller and to disconnect the motor from the internal combustion engine in the event of an internal combustion engine failure; a ribbed flexible belt, for transmitting power from the output shaft of the internal combustion engine to the propeller shaft via the outside of the electric motor, single directionally connected to said sprag clutch; an out-runner electric motor, for transmitting rotary power to the propeller shaft and to switch to a generator to provide power for accessories and to recharge the batteries, rigidly connected to said flexible belt, and rigidly connected to said propeller; and an engine output shaft, for transferring rotary motion to the sprag clutch, rigidly connected to said sprag clutch, and rigidly connected to said internal combustion engine. 